Download INSTALLATION MANUAL AND OPERATING INSTRUCTIONS

INSTALLATION MANUAL AND
OPERATING INSTRUCTIONS
MD200-302/303/306/307 Series
COURSE DEVIATION INDICATOR
MID-CONTINENT INST. CO., INC
MANUAL NUMBER 8017972
th
9400 E. 34 Street N. Wichita, KS 67226 USA
REV. 3 Dec. 15, 2003
Phone 316-630-0101 • Fax 316-630-0723
Revisions
Rev.
Date
Description of Change
1
8/11/00 Corrected typographical errors, added section 4.2
Annunciator Dimming Adjustment
2
4/11/02 Added MD200-302(5V), -303(5V), -306(5V),
-307(5V) indicators. These units have 5 volt bezel
lighting.
3
12/15/03 Corrected 5 volt lighting connections to J1
REV. 3 Dec 15, 2003
ECO#
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2
TABLE OF CONTENTS
SECTION 1
1.1
1.2
1.2.1
1.2.2
1.2.3
1.2.4
1.2.4.1
1.2.4.2
1.2.5
1.2.6
1.2.7
GENERAL DESCRIPTION
INTRODUCTION
SPECIFICATIONS, TECHNICAL
PHYSICAL CHARACTERISTICS
ENVIRONMENTAL CHARACTERISTICS
SPECIFICATIONS, ELECTRICAL
FRONT PANEL CONTROLS
CONTROLS
ANNUNCIATIONS
INTERFACE
EQUIPMENT LIMITATIONS
MAJOR COMPONENTS
SECTION 2
2.1
2.2
2.3
INSTALLATION CONSIDERATIONS
COOLING
EQUIPMENT LOCATION
ROUTING OF CABLES
SECTION 3
3.1
3.2
3.3
3.4
INSTALLATION PROCEDURE
GENERAL INFORMATION
UNPACKING AND INSPECTING
MOUNTING THE MD200-( )
INSTALLATION LIMITATIONS
SECTION 4
4.1
4.2
POST INSTALLATION CHECKOUT
PRE-INSTALLATION TEST
OPERATING INSTRUCTIONS
FIGURE NO.
LIST OF ILLUSTRATIONS
3.1
3.2
3.3
3.4
3.5
MATING CONNECTORS
CUTOUT DEMENSIONS FOR PANEL MOUNTING
MD200-302/303/306/307 SERIES OUTLINE DRAWING
MD200-306/307 SERIES WIRING DIAGRAM
MD200-302/303 SERIES WIRING DIAGRAM
APPENDIX
ENVIRONMENTAL QUALIFICATION FORM
REV. 3 Dec 15, 2003
3
SECTION 1 GENERAL DESCRIPTION
1.1
INTRODUCTION
The Mid-Continent Instruments MD200-302/303/306/307 Nav Indicator is designed to
operate with VHF, and GPS navigational equipment to provide OMNI (VOR), GPS,
LOCALIZER (LOC) and Glideslope (GS) information.
The MD200-302/303 is designed to accept DC Left-Right, To-From and Nav warn flag
signals from a remote mounted VOR converter. Additionally, the MD200-306/307 will
accept DC signals from a glideslope receiver which will drive the UP-DOWN needle along
with a GS warn meter. Both units incorporate NAV, GPS and BC annunciation with
photocell dimming.
When GPS is selected for display, the MD200-( ) receives inputs from compatible
GPS/navigation receivers or Flight Management Systems to provide a visual presentation
to the pilot. All information presented on the navigation indicator is generated from this
external receiver.
Course datum information is offered on the MD200-303 and -307 versions. The course
resolver is ORZ zero’ed to industry standard 300 deg.
Five volt bezel lighting is offered with the MD200-302(5V), -303(5V), -306(5V),
307(5V) indicators.
1.2
-
SPECIFICATIONS, TECHNICAL
1.2.1 PHYSICAL CHARACTERISTICS
Size
Mounting:
Width:
Height:
Depth:
Weight:
REV. 3 Dec 15, 2003
MD200-302/303/306/307
3 1/8 inch Round
Panel
3.25 Inches
3.25 Inches
4.75 Inches max
MD200-302
1.4 lbs.
MD200-303
1.5 lbs.
MD200-306
1.4 lbs.
MD200-307
1.5 lbs.
4
1.2.2 ENVIRONMENTAL CHARACTERISTICS
TSO Compliance:
Applicable Documents:
Operating Temperature Range:
Humidity:
Altitude Range:
Vibration:
Operational Shock:
1.2.3
TSO C34e, C36e, C40c
RTCA DO-160B, DO-192,
DO-195, DO-196
-55°C to +70°C
95% Non-Condensing
0 to 55,000 ft.
Cat. M and N
Rigid Mounting, 6 G Operational
15 G Crash Safety.
SPECIFICATIONS, ELECTRICAL
1.2.3.1 GENERAL
DESIGN:
OPERATING CURRENT:
MD200-302
MD200-303
MD200-306
MD200-307
All Solid State
0.30 Amps
0.30 Amps
0.30 Amps
0.30 Amps
1.2.3.2 VOR/LOC/GPS:
OBS RESOLVER:
Electrical zero: 300 degrees, ORZ.
DEVIATION:
Input impedance: 1K ohms +-10%.
Deflection sensitivity: 150mV +-10%
for full scale deflection.
VALID FLAG:
Input impedance: 1K ohms +-10%
Flag sensitivity: 125mV +10% for flag
to leave stop, 260mV +-10%
maximum, flag fully concealed
TO/FROM FLAG:
200 ohms +-10%. +-40mV +-15% at
25°C flag fully in view.
COURSE DATUM: MD200-303, -307
Standard Arinc X, Y, Z 11.8 VRMS
.030 Amp, 400 Hz
REV. 3 Dec 15, 2003
5
1.2.3.3 GLIDESLOPE: MD200-306, -307 only
DEVIATION:
Input Impedance: 1K ohms +/-10%
Deflection sensitivity: 150mV
+/-10% for full scale deflection.
VALID FLAG:
Input Impedance: 1K ohms +/-10%
Flag sensitivity: 125mV +10% for
flag to leave stop. 260mV +/- 10%
maximum flag fully concealed.
1.2.4 FRONT PANEL CONTROLS
1.2.4.1 CONTROLS:
OBS:
Used to select appropriate inbound or
outbound bearing to a VOR station or
waypoint.
1.2.5 INTERFACE:
NAV/LOC/GPS:
Receives vertical, lateral deviation, warn flags
TO/FROM and OBS resolver information
from the GPS/NAV receiver.
GLIDESLOPE:
Receives GS up-down and warn flag input
from glideslope receiver.
REV. 3 Dec 15, 2003
6
1.2.6 EQUIPMENT LIMITATIONS
1.
2.
3.
4.
5.
REQUIRMENTS FOR TSO’D VOR/ILS SYSTEM:
The navigation receiver shall be certified to the standards of TSO C40a/b/c or TSO
C36c/d/e.
VOR phase error shall not exceed 1.5 degrees.
Variation in VOR composite output not to exceed ±3dB from .500VRMS as the RF input
level of a standard VOR test signal to the receiver is varied from 10uV to 10,000uV.
Variation in the LOC composite output not to exceed ±2dB from .333VRMS as the RF
input level of a standard localizer test signal to the receiver is varied from 50uV to
10,000uV.
A control line (ILS Energize) must be provided as a low impedance to ground when an
ILS frequency is selected.
REQUIRMENTS FOR TSO’D GLIDESLOPE SYSTEM:
1. The glideslope receiver/converter shall be certified to the standards of TSO C34c/d/e.
2. The centering error as presented to the pilot shall not exceed 13% of standard deflection
with a 95% probability under all combinations of the service conditions listed
in RTCA paper DO-192.
3. Deviation current with a 700uV standard glideslope deviation signal applied to the
receiver input shall be 78uA ±10% into a 1000 ohm load. Deviation current shall not
change more than 15% as the RF level of a standard glideslope deviation signal is varied
from 100 to 10,000uA. Deviation current shall be proportional within 5% to the difference
in depth of modulation of the 90Hz and 150Hz tones.
3. Warning signal output shall be a DC current less than 125uA into a 1000 ohm load for a
warning flag to be fully visible. Warning signal for a fully concealed warning flag shall be
a DC current of 260uA minimum into a 1000 ohm load.
1.2.7 MAJOR COMPONENTS
The system is comprised of one major component, the MD200-( ) Course Deviation Indicator.
REV. 3 Dec 15, 2003
7
SECTION 2 INSTALLATION CONSIDERATIONS
2.1
COOLING
No direct cooling is required. As with any electronic equipment, overall reliability may be
increased if the MD200-( ) is not located near any high heat source or crowded next to other
equipment.
2.2
EQUIPMENT LOCATION
The MD200-( ) course deviation indicator must be mounted as close to the pilot’s field of
view as possible. The unit depth, with connector attached, must also be taken into
consideration.
2.3
ROUTING OF CABLES
Care must be taken not to bundle the MD200-( ) logic and low level signal lines with any high
energy sources. Examples of these sources include 400 HZ AC, Comm, DME, HF and
transponder transmitter coax. Always use shielded wire when shown on the installation print.
Avoid sharp bends in cabling and routing near aircraft control cables.
REV. 3 Dec 15, 2003
8
SECTION 3 INSTALLATION PROCEDURES
3.1
GENERAL INFORMATION
This section contains interconnect diagrams, mounting dimensions and other information
pertaining to the installation of the MD200-( ). After installation of cabling and before
installation of the equipment, ensure that power is applied only to the pins specified in the
interconnect diagram.
3.2
UNPACKING AND INSPECTING EQUIPMENT
When unpacking equipment, make a visual inspection for evidence of damage incurred during
shipment. The following parts should be included:
1.
2.
3.
4.
3.3
MD200-( ) Series course Deviation Indicator
Connector Kit (9 pin). MCI P/N 8017287 (-303, 307 only)
Connector Kit (25 pin). MCI P/N 7014517
Installation Manual. MCI P/N 8017972
MOUNTING THE MD200-( )INDICATOR
Plan a location in the aircraft for the MD200-( ) course deviation indicator to be mounted as
close to the pilot’s field of view as possible. Avoid mounting close to heater vents or other
high heat sources. Allow a clearance of at least 3 inches from back of unit for plug removal.
The indicator is secured in place behind the panel since it is designed for rear mount only.
Make a panel cutout as shown in Figure 3.2. Secure the indicator in place with three 6-32 x
1.0” flat head phillips screws.
3.4
INSTALLATION LIMITATIONS
Wire the aircraft harness according to the appropriate figure. Use at least 24 AWG wire for all
connections. You MUST use shielded wire where shown by the receiver manufacture. Avoid
sharp bends and routing cable near high energy sources. Care must be taken to tie the harness
away from aircraft controls and cables.
REV. 3 Dec 15, 2003
9
FIGURE 3-1 REAR VIEW OF MATING CONNECTORS
FIGURE 3-2 CUTOUT DIMENSIONS FOR PANEL MOUNTING
REV. 3 Dec 15, 2003
10
FIGURE 3-3 OUTLINE DRAWING
REV. 3 Dec 15, 2003
11
FIGURE 3-4 WIRING DIAGRAM, MD200-302/303
FIGURE 3-5 WIRING DIAGRAM, MD200-306/307
REV. 3 Dec 15, 2003
12
SECTION 4 POST INSTALLATION CHECK
4.1
PRE INSTALLATION TESTS
With the MD200-( ) disconnected, turn on the avionics master switch and verify that aircraft
power on J1 pin 19 is 14Vdc or pin 20 is 28Vdc. Using an ohmmeter, verify pin 21 is aircraft
ground.
4.2
ANNUNCIATOR DIMMING ADJUSTMENT
Following installation of the MD200-( ) CDI, check the brightness of the GPS, NAV and BC
annunciations as necessary with the ambient and aircraft panel lighting levels set to simulate
minimum-light operations. If required, the dimming adjustment is located on the side of the
MD200-( ) unit, and is labeled “ANNUN DIM ADJ”.
4.3
OPERATING INSTRUCTIONS
All controls required to operate the MD200-( ) course deviation indicator are located on the
unit’s front panel and on the front panel of the related navigation receiver.
4.3.1 VOR OPERATION
Channel the NAV receiver to the desired VOR frequency and positively identify the station by
listening to received audio. Determine the NAV warning flag is out of view.
Flying inbound to a VOR station is accomplished by first rotating the OBS knob to center the
deviation indicator, and determining the TO-FROM meter is in the TO condition. The aircraft
is then turned to a magnetic heading which is the same as the selected course with proper
allowance for wind correction. When the aircraft is on course, the vertical pointer will be
centered. If the aircraft moves off course, the deviation indicator will move away from the
center position and flying in the direction of pointer deflection (left or right) is required to reintercept the course.
The procedure for flying outbound from a VOR station is the same as flying inbound, except
the OBS knob is first rotated to cause a “FROM” indication to appear with the pointer
centered.
To intercept a selected VOR radial (from the station) and fly outbound, turn the OBS control
to set the desired radial under the top indicator index. Maneuver the aircraft to fly the selected
radial magnetic heading plus 45° intercept angle which will provide a sufficient intercept
angle. The intercept angle should be reduced as the deviation needle approaches an on course
condition (center) to prevent excessive course bracketing.
4.3.2 LOCALIZER OPERATION
REV. 3 Dec 15, 2003
13
Select the desired localizer frequency and observe that the localizer warning flag is concealed.
The TO-FROM flag is not functional for localizer operation. When flying on the front course
or outbound on the back course make corrections toward the localizer (vertical) needle
deflection. The localizer path narrows as the approach end of the runway becomes closer.
When flying inbound on the back-course or outbound on the front course, the corrections are
made away from the direction of needle deflection. A helpful hint when flying the localizer is
to set the localizer heading on the OBS dial under the lubber line for quick reference.
4.2.3 GLIDESLOPE OPERATION
The glideslope (horizontal) needle provides the pilot with vertical steering information during
ILS approaches. The glideslope circuitry is energized when the associated localizer frequency
is selected on the navigation receiver. Observe that the glideslope warning flag is concealed.
The glideslope needle deflects towards the direction the pilot must fly to remain on the glide
path.
If the glideslope needle deflects upward the aircraft is below the glide path and the pilot must
climb to again intercept the glide path and center the needle. If the needle deflects downward
the aircraft is above the glide path and the pilot must descend to again intercept the glide path
and center the needle. When the needle is centered the aircraft is on the glide path.
REV. 3 Dec 15, 2003
14
ENVIRONMENTAL QUALIFICATION FORM
RTCA / DO160B
NOMENCLATURE: MD200-( ) COURSE DEVIATION INDICATOR
MODEL NO: MD200-( )
TSO NO: C34e
C36e, C40c
MANUFACTURER TEST SPECIFICATION:
MPS 8014565
MANUFACTURER: MID-CONTINENT INSTRUMENT CO., INC.
9400 E 34 Street N.
WICHITA, KS 67226 PHONE (316) 630-0101
Conditions
Temperature and Altitude
Low Temperature
High Temperature
Altitude
Decompression
Overpressure
Section
Description of Conducted Tests
4.0
Equipment tested to Categories F2 except as noted
4.5.1
4.5.2 & 4.5.3
4.6.1
4.6.2
Not Tested
4.6.3
Not Tested
Temperature Variation
5.3
Equipment tested to Category B
Humidity
6.0
Equipment tested to Category A
7.0
7.2.1
7.3.1
Equipment tested per DO-160B
Shock
Operational
Crash Safety
Vibration
8.0
Equipment tested without shockmounts to Categories M
and N
(Table 8-1)
Explosion
9.0
Equipment identified as Category X, no test required
Waterproofness
10.0
Equipment identified as Category X , no test required
Fluids Susceptibility
11.0
Equipment identified as Category X, no test required
REV. 3 Dec 15, 2003
15
Environmental Qualification (cont.)
Conditions
Section
Description of Conducted Tests
Sand and Dust
12.0
Equipment identified as Category X, no test required
Fungus
13.0
Equipment identified as Category X, no test required
Salt Spray
14.0
Equipment identified as Category X, no test required
Magnetic Effect
15.0
Equipment tested to Class A
Power Input
16.0
Equipment tested to Category B
Voltage Spike
17.0
Equipment tested to Category B
Audio Frequency
Susceptibility
Induced Signal Susceptibility
18.0
Equipment tested to Category B
19.0
Equipment tested to Category B
Radio Frequency
Susceptibility
Radio Frequency Emissions
20.0
Equipment tested to Category B
21.0
Equipment tested to Category B
Lightning Induced Transient
Susceptibility
Lightning Direct Effects
Icing
22.0
Equipment identified as Category X, no test required
23.0
24.0
Equipment identified as Category X, no test required
Equipment identified as Category X, no test required
REV. 3 Dec 15, 2003
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